GB1022386A - Improvements in a rotor assembly for turbine and like bladed machines - Google Patents

Improvements in a rotor assembly for turbine and like bladed machines

Info

Publication number
GB1022386A
GB1022386A GB20791/64A GB2079164A GB1022386A GB 1022386 A GB1022386 A GB 1022386A GB 20791/64 A GB20791/64 A GB 20791/64A GB 2079164 A GB2079164 A GB 2079164A GB 1022386 A GB1022386 A GB 1022386A
Authority
GB
United Kingdom
Prior art keywords
slot
root
turbine
spacer
rotor assembly
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB20791/64A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of GB1022386A publication Critical patent/GB1022386A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,022,386. Cotters. GENERAL ELECTRIC CO. May 20, 1964 [Oct. 24, 1963], No. 20791/64. Heading F2H. [Also in Division F1] The root 14 of an aerofoil blade 10 is mounted in an axial slot 30 in a rotor disc 22. Positioned between the bottom 19 of root 14 and the base 34 of slot 30 is a spacer 61 having an axial slot 66 in the bottom thereof. A locking strip 52 is mounted in slot 66 and its ends 56, 58 are bent to retain the root 14 and spacer 61 axially within slot 30. Root 14 is removed from slot 30 by bending down tab 58, inserting tool 70 in hole 68 to remove spacer 61 and then moving root 14 radially inwards and axially.
GB20791/64A 1963-10-24 1964-05-20 Improvements in a rotor assembly for turbine and like bladed machines Expired GB1022386A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US318557A US3216699A (en) 1963-10-24 1963-10-24 Airfoil member assembly

Publications (1)

Publication Number Publication Date
GB1022386A true GB1022386A (en) 1966-03-09

Family

ID=23238676

Family Applications (1)

Application Number Title Priority Date Filing Date
GB20791/64A Expired GB1022386A (en) 1963-10-24 1964-05-20 Improvements in a rotor assembly for turbine and like bladed machines

Country Status (4)

Country Link
US (1) US3216699A (en)
BE (1) BE654781A (en)
DE (1) DE1426806A1 (en)
GB (1) GB1022386A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1301638B (en) * 1965-07-31 1969-08-21 Rolls Royce Blade ring for gas turbine engines
FR2641031A1 (en) * 1988-12-23 1990-06-29 United Technologies Corp

Families Citing this family (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1119617A (en) * 1966-05-17 1968-07-10 Rolls Royce Compressor blade for a gas turbine engine
US3378230A (en) * 1966-12-16 1968-04-16 Gen Electric Mounting of blades in turbomachine rotors
GB1121194A (en) * 1967-05-01 1968-07-24 Rolls Royce Bladed rotor for a fluid flow machine
US3383095A (en) * 1967-09-12 1968-05-14 Gen Electric Lock for turbomachinery blades
US3508844A (en) * 1968-07-25 1970-04-28 United Aircraft Corp Blade lock
US3653781A (en) * 1970-12-18 1972-04-04 Gen Electric Turbomachinery blade retainer
BE794573A (en) * 1972-02-02 1973-05-16 Gen Electric AUBES FIXING DEVICE
US3832092A (en) * 1973-10-19 1974-08-27 Gen Electric Device for locking turbomachinery blades
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
US4207029A (en) * 1978-06-12 1980-06-10 Avco Corporation Turbine rotor assembly of ceramic blades to metallic disc
US4798519A (en) * 1987-08-24 1989-01-17 United Technologies Corporation Compressor part span shroud
US5460488A (en) * 1994-06-14 1995-10-24 United Technologies Corporation Shrouded fan blade for a turbine engine
US5667361A (en) * 1995-09-14 1997-09-16 United Technologies Corporation Flutter resistant blades, vanes and arrays thereof for a turbomachine
FR2746456B1 (en) * 1996-03-21 1998-04-30 Snecma DEVICE FOR RETAINING THE FOOT OF THE BLADES OF A BLOWER
US5695323A (en) * 1996-04-19 1997-12-09 Westinghouse Electric Corporation Aerodynamically optimized mid-span snubber for combustion turbine blade
US6109877A (en) * 1998-11-23 2000-08-29 Pratt & Whitney Canada Corp. Turbine blade-to-disk retention device
FR2841609B1 (en) * 2002-06-27 2004-09-10 Snecma Moteurs BLOWER RETAINER LEVEL RETAINER
US6837686B2 (en) 2002-09-27 2005-01-04 Pratt & Whitney Canada Corp. Blade retention scheme using a retention tab
GB2408296A (en) * 2003-11-22 2005-05-25 Rolls Royce Plc Compressor blade root retainer with integral sealing means to reduce axial leakage
US20090060746A1 (en) * 2007-08-30 2009-03-05 Honeywell International, Inc. Blade retaining clip
US8287238B2 (en) * 2008-02-29 2012-10-16 General Electric Company Hub pitch gear repair method
US8540488B2 (en) * 2009-12-14 2013-09-24 Siemens Energy, Inc. Turbine blade damping device with controlled loading
USRE45690E1 (en) 2009-12-14 2015-09-29 Siemens Energy, Inc. Turbine blade damping device with controlled loading
US8616848B2 (en) * 2009-12-14 2013-12-31 Siemens Energy, Inc. Turbine blade damping device with controlled loading
FR2963383B1 (en) * 2010-07-27 2016-09-09 Snecma DUST OF TURBOMACHINE, ROTOR, LOW PRESSURE TURBINE AND TURBOMACHINE EQUIPPED WITH SUCH A DAWN
US8851854B2 (en) * 2011-12-16 2014-10-07 United Technologies Corporation Energy absorbent fan blade spacer
US9422819B2 (en) * 2012-12-18 2016-08-23 United Technologies Corporation Rotor blade root spacer for arranging between a rotor disk and a root of a rotor blade
EP2946080B1 (en) 2013-01-17 2018-05-30 United Technologies Corporation Rotor blade root spacer with grip element
DE102013205948B4 (en) * 2013-04-04 2015-03-12 MTU Aero Engines AG Safety system and method for securing a mounting area of at least one rotor blade or a rotor blade segment in a mounting region of a rotor base body
DE102013214933A1 (en) * 2013-07-30 2015-02-26 MTU Aero Engines AG Method for mounting a gas turbine blade in an associated receptacle of a rotor base body
GB201403072D0 (en) * 2014-02-21 2014-04-09 Rolls Royce Plc A rotor for a turbo-machine and a related method
US10215035B2 (en) * 2014-12-29 2019-02-26 Rolls-Royce North American Technologies Inc. Turbine wheels with preloaded blade attachment
US10557356B2 (en) * 2016-11-15 2020-02-11 General Electric Company Combined balance weight and anti-rotation key
FR3093532B1 (en) * 2019-03-06 2021-05-14 Safran Aircraft Engines Device for ventilating a turbine wheel of a turbomachine and / or axial retaining of blades of such a wheel
DE102019210647A1 (en) * 2019-07-18 2021-01-21 Siemens Energy Global GmbH & Co. KG Blade ring for an axial turbo machine
US12018590B1 (en) 2023-04-04 2024-06-25 Ge Infrastructure Technology Llc Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove
US12110809B1 (en) * 2023-04-04 2024-10-08 Ge Infrastructure Technology Llc Turbine blade and assembly with dovetail arrangement for enlarged rotor groove

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2421890A (en) * 1944-11-27 1947-06-10 Goetaverken Ab Turbine blade
DE834408C (en) * 1950-11-23 1952-03-20 Maschf Augsburg Nuernberg Ag Prestressed axial blade root attachment for steam and gas turbines
FR1095392A (en) * 1953-12-01 1955-06-01 Csf Gas turbine blades
US2955799A (en) * 1957-02-11 1960-10-11 United Aircraft Corp Blade damping means

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1301638B (en) * 1965-07-31 1969-08-21 Rolls Royce Blade ring for gas turbine engines
FR2641031A1 (en) * 1988-12-23 1990-06-29 United Technologies Corp

Also Published As

Publication number Publication date
DE1426806A1 (en) 1969-04-10
US3216699A (en) 1965-11-09
BE654781A (en) 1965-02-15

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